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RAF 27 AIRFOIL (raf27-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAF 27 AIRFOIL (raf27-il)
Reynolds number: 50,000
Max Cl/Cd: 27.55 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf27-il-50000-n5.txt
Download as CSV file: xf-raf27-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 27 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6868   0.09225   0.08508  -0.0187   1.0000   0.0483
 -10.750  -0.7032   0.08482   0.07766  -0.0237   1.0000   0.0478
 -10.500  -0.7235   0.07806   0.07087  -0.0281   1.0000   0.0472
 -10.250  -0.7449   0.07250   0.06524  -0.0308   1.0000   0.0467
 -10.000  -0.7664   0.06797   0.06058  -0.0313   1.0000   0.0464
  -9.750  -0.7857   0.06414   0.05660  -0.0299   1.0000   0.0464
  -9.500  -0.7993   0.06025   0.05246  -0.0284   1.0000   0.0465
  -9.250  -0.8085   0.05636   0.04824  -0.0265   1.0000   0.0470
  -9.000  -0.8128   0.05254   0.04401  -0.0245   1.0000   0.0476
  -8.750  -0.8120   0.04889   0.03989  -0.0224   1.0000   0.0485
  -8.500  -0.8073   0.04555   0.03596  -0.0201   1.0000   0.0500
  -8.250  -0.7956   0.04300   0.03337  -0.0188   1.0000   0.0531
  -8.000  -0.7821   0.04071   0.03077  -0.0173   1.0000   0.0567
  -7.750  -0.7660   0.03805   0.02768  -0.0157   1.0000   0.0599
  -7.500  -0.7483   0.03575   0.02506  -0.0142   1.0000   0.0647
  -7.250  -0.7300   0.03399   0.02319  -0.0130   1.0000   0.0711
  -7.000  -0.7080   0.03202   0.02088  -0.0117   1.0000   0.0771
  -6.750  -0.6893   0.03050   0.01936  -0.0104   1.0000   0.0863
  -6.500  -0.6690   0.02890   0.01768  -0.0091   1.0000   0.0951
  -6.250  -0.6492   0.02745   0.01606  -0.0075   1.0000   0.1052
  -6.000  -0.6322   0.02611   0.01479  -0.0059   1.0000   0.1220
  -5.750  -0.6151   0.02476   0.01351  -0.0042   1.0000   0.1438
  -5.500  -0.5987   0.02340   0.01237  -0.0025   1.0000   0.1766
  -5.250  -0.5836   0.02213   0.01144  -0.0007   1.0000   0.2369
  -5.000  -0.5696   0.02103   0.01076   0.0014   1.0000   0.3168
  -4.750  -0.5557   0.02019   0.01028   0.0039   1.0000   0.3974
  -4.500  -0.5398   0.01960   0.00991   0.0064   1.0000   0.4666
  -4.250  -0.5228   0.01914   0.00959   0.0089   1.0000   0.5225
  -4.000  -0.5056   0.01881   0.00943   0.0117   1.0000   0.5795
  -3.750  -0.4881   0.01860   0.00933   0.0146   1.0000   0.6363
  -3.500  -0.4693   0.01845   0.00920   0.0172   1.0000   0.6858
  -3.250  -0.4466   0.01831   0.00905   0.0191   1.0000   0.7233
  -3.000  -0.4227   0.01820   0.00887   0.0206   1.0000   0.7574
  -2.750  -0.3965   0.01814   0.00870   0.0216   1.0000   0.7901
  -2.500  -0.3657   0.01815   0.00862   0.0217   1.0000   0.8209
  -2.250  -0.3312   0.01820   0.00855   0.0210   1.0000   0.8504
  -2.000  -0.2926   0.01829   0.00848   0.0193   1.0000   0.8781
  -1.750  -0.2474   0.01841   0.00845   0.0162   1.0000   0.9028
  -1.500  -0.1977   0.01850   0.00837   0.0120   1.0000   0.9247
  -1.250  -0.1471   0.01851   0.00826   0.0074   1.0000   0.9452
  -1.000  -0.0984   0.01844   0.00808   0.0028   1.0000   0.9652
  -0.750  -0.0495   0.01830   0.00787  -0.0022   1.0000   0.9837
  -0.500  -0.0010   0.01810   0.00763  -0.0073   1.0000   1.0000
  -0.250   0.0002   0.01798   0.00753  -0.0038   1.0000   1.0000
   0.000   0.0000   0.01793   0.00749   0.0000   1.0000   1.0000
   0.250  -0.0003   0.01798   0.00753   0.0038   1.0000   1.0000
   0.500   0.0010   0.01810   0.00763   0.0073   1.0000   1.0000
   0.750   0.0493   0.01830   0.00787   0.0022   0.9837   1.0000
   1.000   0.0983   0.01844   0.00808  -0.0028   0.9653   1.0000
   1.250   0.1470   0.01851   0.00825  -0.0074   0.9452   1.0000
   1.500   0.1977   0.01849   0.00837  -0.0120   0.9247   1.0000
   1.750   0.2473   0.01841   0.00845  -0.0162   0.9028   1.0000
   2.000   0.2925   0.01829   0.00848  -0.0193   0.8782   1.0000
   2.250   0.3311   0.01820   0.00855  -0.0210   0.8504   1.0000
   2.500   0.3657   0.01815   0.00861  -0.0217   0.8209   1.0000
   2.750   0.3964   0.01814   0.00870  -0.0216   0.7901   1.0000
   3.000   0.4225   0.01820   0.00886  -0.0205   0.7574   1.0000
   3.250   0.4465   0.01831   0.00904  -0.0191   0.7233   1.0000
   3.500   0.4692   0.01844   0.00920  -0.0172   0.6858   1.0000
   3.750   0.4880   0.01860   0.00933  -0.0146   0.6363   1.0000
   4.000   0.5055   0.01881   0.00943  -0.0116   0.5795   1.0000
   4.250   0.5227   0.01914   0.00959  -0.0089   0.5224   1.0000
   4.500   0.5397   0.01959   0.00990  -0.0064   0.4666   1.0000
   4.750   0.5557   0.02018   0.01028  -0.0039   0.3979   1.0000
   5.000   0.5695   0.02103   0.01075  -0.0014   0.3168   1.0000
   5.250   0.5835   0.02212   0.01144   0.0007   0.2372   1.0000
   5.500   0.5987   0.02340   0.01236   0.0025   0.1766   1.0000
   5.750   0.6150   0.02476   0.01351   0.0042   0.1439   1.0000
   6.000   0.6321   0.02611   0.01478   0.0059   0.1215   1.0000
   6.500   0.6690   0.02889   0.01768   0.0091   0.0951   1.0000
   6.750   0.6893   0.03050   0.01936   0.0104   0.0863   1.0000
   7.000   0.7081   0.03203   0.02089   0.0117   0.0771   1.0000
   7.250   0.7301   0.03400   0.02320   0.0130   0.0710   1.0000
   7.500   0.7484   0.03576   0.02507   0.0142   0.0647   1.0000
   7.750   0.7661   0.03805   0.02767   0.0156   0.0599   1.0000
   8.000   0.7822   0.04072   0.03078   0.0173   0.0567   1.0000
   8.250   0.7957   0.04302   0.03340   0.0188   0.0532   1.0000
   8.500   0.8078   0.04556   0.03595   0.0201   0.0501   1.0000
   8.750   0.8119   0.04893   0.03995   0.0224   0.0484   1.0000
   9.000   0.8130   0.05256   0.04403   0.0245   0.0476   1.0000
   9.250   0.8088   0.05637   0.04825   0.0265   0.0470   1.0000
   9.500   0.7997   0.06027   0.05248   0.0283   0.0465   1.0000
   9.750   0.7863   0.06414   0.05659   0.0298   0.0463   1.0000
  10.000   0.7665   0.06801   0.06063   0.0312   0.0463   1.0000
  10.250   0.7453   0.07254   0.06527   0.0307   0.0467   1.0000
  10.500   0.7245   0.07804   0.07085   0.0280   0.0472   1.0000
  10.750   0.7038   0.08489   0.07772   0.0235   0.0478   1.0000
  11.000   0.6881   0.09218   0.08501   0.0187   0.0484   1.0000
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